Aerodynamic Loads on an Isolated Shrouded-propeller Configuration of Angles of Attack from -10 Degrees to 110 Degrees PDF Download
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Author: Kalman J. Grunwald
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 36
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Book Description
Author: Kalman J. Grunwald
Publisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 36
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 1166
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Book Description
Author: Dietrich Knoerzer
Publisher: Springer Nature
ISBN: 3031120191
Category : Technology & Engineering
Languages : en
Pages : 290
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Book Description
This book provides research results using computational methods for fluid dynamics and engineering problems in aeronautics and other scientific and industrial applications. It gives an overview on the state of the art and the technology trends requiring advanced computational methods towards digitization in industrial and scientific processes. The chapters are based on Special Technology Sessions of the WCCM-ECCOMAS Virtual Congress 2021.
Author:
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 1170
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 816
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Book Description
Author: Douglas Aircraft Company
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 690
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Book Description
Author: John W. Draper
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82
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Book Description
This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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Book Description
"An investigation of the aerodynamic characteristics of a powered semispan tilting-shrouded-propeller configuration has been conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. The wing had an aspect ratio of 2.67 (based on wing span of 60 inches), a taper ratio of 0.67, and an NACA 2418 airfoil section with a 15-inch-diameter shrouded propeller mounted on the tip. The test results show that large nose-up pitching moments are obtained at transitional speeds of about 40 knots and duct angle of about 70°. Decelerating flight procedures further increases in the nose-up moment. Ground proximity reduces the nose-up pitching moments. The large nose-up moments can be trimmed by use of duct-exit control vanes. The results show that unloading the duct (shroud) by flying at a wing angle of attack of 15° reduces the power required by about 30 percent at 50 knots. Duct-lip stall produces large increases in power required. The results in general show that full-scale aerodynamic simulation can be made with small-scale wind-tunnel models if duct-lip separation at low Reynolds numbers is avoided."--Summary.
Author: George G. Edwards
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 658
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Book Description
An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.
Author: William A. Newsom
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 714
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Book Description
An investigation has been made to determine the effect of propeller location and flap deflection on the lift, drag, and pitching-moment characteristics of a wing-propeller combination over an angle-of-attack range from 0 to 80 degrees. The model had four propellers, the slipstream from which covered practically the entire span of the wing. The wing had a 30-percent-chord slotted flap and an 8.5-percent-chord slat. Data were obtained for flap deflections of 0, 20, 40, and 60 degrees with the slat off and on. For one propeller position the power input to the model was measured and tuft studies of the flow on the wing were made. The data are analyzed to assess the feasibility, from consideration of stability and control, of a tilting-wing vertical-take-off-and-landing airplane with the wing pivoted behind the primary wing structure to provide a desirable structural configuration. The main object of the investigation was to determine whether advantage might be taken of the forward shift of the center of gravity of the airplane, as the wing is tilted from an angle of attack of 90 to 0 degrees, to minimize the change in trim pitching moment throughout the transition speed range for such a configuration. The results indicate that with proper propeller position and programming of flap deflection, it is possible to design a configuration of this type in which essentially no change in trim is required throughout the transition from hovering to normal unstalled forward flight.
